Aeroplane.



J. WATTS.

AEROPLANE. APPLICATION HLED JULY 10. 1912.

PatentedSept. 14, 1915.

6 SHEETS-SHEET I.

J. WATTS.

AEROPLANE.

APPLICATION FILED JULY 10, 19I2.

6 SHEETS-SHEET 2.

Patented Sept. 14, 1915.

L'WATTS. AEROPjLANE.

' APPLICATION FILED JULY 10, 1912. I 1,153,659, Patented Sept. 14, 1915.

6 SHEETSSHEET 3.

J. WATTS. AEROPLANE.

I I APPLICATION FILED JULY 10, H2. 1,153,659. Patented Sept. 14, 1915.

6 SHEETS-SHEET 4.

- (Ewan/am J. WATTS.

AEROPLANE.

APPLICATION EILEDIULY 10. 1912.

Patented Sept. 14, 1915.

6 SHEETSSHEET 5.

J. WATTS. AEROPLANE. APPLICATION FILED JULY 10. I912.

Patgnted Sept. 14, 1915.

6 SHEETS -SHEET 6- JOHN WATTS, OF KANSAS CITY, MISSOURI.

AEROPL AN E.

Specification of Letters Patent.

Patented Sept. 14, 19315.

Application filed July 10, 1912. Serial No. 708,549.

To all whom it may concern.

Be it known that I, JOHN WATTS, a citizen of the United States, residing at Kansas City, in the county of Jackson and State of Missouri, have invented certain new and useful Improvements in Aeroplanes, of which the following is a specification.

This invention relates to aeroplanes, and has for its object to produce a machine having hinged wing planes and means whereby they may be swung to and held in a substantially horizontal position or to and held at different dihedral angles while in flight.

A further object is to produce a control column movable in one direction to simultaneously effect a change of the wings and the raising of the horizontal rudder and in the reverse direction to effect the restoration of said parts to normal position.

Another object is to minimize bucking of the machine by holding the wings in flight position under a yielding pressure so that they shall largely relieve the machine as a whole of the sudden shock or jar invariably met with during flight in windy or gusty weather and thereby minimize danger of dislodgment of the operator from his seat.

Another object is to produce a machine having wings provided at their outer ends with foldable tips and means whereby the operator is enabled to collapse either of the tips for. the purpose of restoring the equilibrium of the machine. 7

With these objects in view, the invention consists in certain novel .and peculiar features of construction and organization as hereinafter described and claimed; and in order that it may be .fully understood reference is to be had to the accompanying drawings, in which Figure 1, is a broken plan view of a monoplane embodying my invention. Fig. 2, is a side view ofthe front end of the machine,

on a larger scale than Fig. 1. Fig. 3, is avertical section on the line III-III of Fig. 2, with the seat omitted. Fig. 4, is a diagrammatic view of the rear portion of the wing control connections as viewed from the rear thereof. Fig. 5, is a similar view of the front portion of the wing control connections. Fig. 6, is a section on the .dotted line VI of Fig. 2. Fig. 7, is a section on the dotted line VII of Fig. 2. Fig. 8, is a vertical section of the connection between an air cylinder and piston thereof and a guide for the piston in its reciprocatory action. Fig. 9, is

on the line IXIX of Fig. 1. Fig. 10, is

a section on the dotted line X of Fig. 2.

Fig. 11, is a side view of the rear end of the fuselage, the stabilizing'planes and the Vertical and horizontal rudder. Fig. 12, is a fragmentary horizontal section showing the means for collapsing one of the wing tips. Fig. 13, is a vertical section on the line XIII-XIII of Fig. 12. Fig. 14, is a detail perspective view showing the means for holding the wing tips yieldingly spread or expanded. Fig. 15, is a section on the line XV of Fig. 1. Fig. 16 is a diagrammatic perspective view of the connections leading from the control column. Fig. 17, is a cross section through the compensating pulleys hereinafter referred to.

Referring first to the construction of the fuselage, a pair of bars consists of portions 1 fitting flatly together and portions 2 spaced apart,- the adjacent ends of portions 1 and 2 being connected together by curved portions 3, and the front ends of portions 2 by inwardly-bowed portions 4. Centrally below portions 1 is a bar 5, which terminates short .of the front or bowed ends of portions 2, and

secured to' the front end of bar 5 is a pair of bowed upwardly-diverging bars 6, which terminate in a horizontal plane below the bowed portions 4 of portions 2. Vertically below portions 2, in the horizontal plane of the upper ends of curved bars 6, is a pair of horizontal bars 7 which, at their front ends,

bow inward at 8 and are secured in any.

suitable manner to the upper ends of bars 6. Bars 7 from a point rearward of curved portions 3, converge rearwardly to a point in the vertical plane of the rear ends of portions 1, and said bars 7 are connected rigidly to bar 5 by a series of downwardly converging struts 9, and to portions 2 by vertical struts 10, and to portions 1 by upwardly converging struts 11. The rear ends of bars 1 are fastened to a short vertical bar 12, and the rear end of bar 5 is fastened to the lower end of said bar 12, the intermediate rearward-converging bars 7 being also fastened at their rear extremities to said bar 12, the various parts described cooperating with suitable wire bracing shown in Figs. 1 and 11, to produce a light, strong and rigid fuselage.

Underlying bar 5 and projecting beyond the front end of the fuselage is a skid 13,111)- turned at its front end, and connecting said 42 preferably sides of the fuselage,

' connected by a plurality of fore and aft ribs skid with bar 5 is a pair of braces 14 and 15, bya coiled spring 47 attached to a cross bar the skid being braced against lateral move 48 bridging portions 2 'of the fuselage. ment by a pair of downwardly-converging These loops 44 and sheaves 45 and 46 conbraces 16, secured at their upper ends to bars stitute a block and tackle mechanism where- 7, and secured to and extending transversely by a short movement of sheaves 46 toward of the skid, is a resilient axle 17, preferably sheaves 45, permits of the folding of either of the leaf-spring type, and journaled on of the wing tips and a corresponding rethe ends of said axle is a pair of wheels 18, verse movement of said sheaves 46 results in the ends of the axle being also connected by the unfolding of the folded tips, it being wires 19 to the bars 7 of the fuselage. noted by reference to Fig. 1, that the outer 20 is a motor of any suitable or preferred portions of the cable 41 extend around guide type, supported in the front end of the fusesheaves 49 at the outer front corners of the lage, and 21 is the propeller to be driven by Wings, and that said spring when unresisted, the motor. At the rear end of the fuselage is holds said tips in unfolded or normal posia 'suitaably-journaled rudder post 22, and tion. mounted thereon is the rudder 23 whereby The cables 42 extend from the inner ends the machine is steered to the right or left, of the tubular spars 30, across the fuselage, and projecting toward opposite sides from and each is formed with a plurality of loops the rudder post are arms 24, whereby the 50, and is attached at its inner end to the adjustment of the rudder is effected by suitsupport or strut 36 at the side of the fuseable connections hereinafter referred to. lage most remote from the connected wing 25 is a pair of horizontal stabilizing tip. The outer portions of the loops engage planes rigid with and disposed at opposite superposed sheaves 51 attached to the adand hinged thereto jacent strut 36 and the inner ends of said is a horizontal rudder 26, and projecting loops engage superposed sheaves 52 carried upward and downward from said rudder 26 by an upright control column 53,- it being are braced arms 27, which through connecunderstood that the two sets of sheaves 51 tions hereinafter described, are utilized to and 52 constitute block and tacklemecharaise or lower the rudder 26 to aid in efl'ectnisms whereby to impart to or accommodate ing upward and downward movement rerelatively long movements of the wing tips spectively, of the machine. through lateral swinging movement of the 28 indicates the wings, each consisting of control column, it being also understood that a front spar 29 and rear tubular spar 30, the operation of one tip does not affect the otheras the cable 41 pays out or takes 31 and a fabric cover 32. At their inner up to accommodate the collapse or unfoldends and paralleling the ribs, the wings are ing of either tip. equipped with tubes 33 pivotally engaging The control column is composed of an upbrackets 34 (Fig. 1), secured to portions 2 per and alower section pivoted together to of the fuselage, and supports 35; the latter permit the former which carries sheaves 52, being shown as brackets secured to struts 36 to swing laterally. And near the upper end of the fuselage, (Fig. 2), it being noted that of the lower section, the column is pivoted the said hinge connections between the inner at 54 to swing longitudinally, being pivoted ends of the wings and the fuselage are to a bracket 55 mounted on a cross-bar 56 inclined upward slightly, to the horizontal. connecting and supported by a pair of the At the outer ends of the wings and carried struts 9. The lower end of the column thereby are foldable wing-tips 37 the same fits into a wedge clamp, consisting of a pair consisting of a series of forked ribs 38 arof plates 57 bowed toward each other and ranged in fan-like relation and pivoted topivoted at 58 for movement in a horizontal gether at their front ends at 39 at or near plane, to a T-shaped post 59 mounted upon the front outer corners of the wings, and a the bar 5. The function of this clamp is flexible cover 40, the forked ribs guarding hereinafter explained. against upward flexing of the tips while By imparting longitudinal swinging spread in flight. To effect the unfolding or movement to the column, the horizontal rudfolding of wing tips, cables 41 and 42 are ders are raised or lowered through suitablysecured to the outermost ribs 38, the cables guided cables 60 attached to their front extending through eyes or ends to the column above and below its pivguides 43 of the remaining ribs and through otal point 54, and at their rear ends to the rear or tubular spars 30 of the wings. branched cables 61 connected to the arms The cable 41, centrally between its ex- 27 hereinbefore described. These cables tremities where it is attached to the outerwill preferably be crossed so that rearward most ribs of the foldable tips, is formed with movement of the upper end of the column a plurality of loops 44 arranged around a will raise the horizontal rudders and reverse series of fixed superposed sheaves 45 and a movement ,will lower the same, the lower corresponding numberof movable sheaves end of the column at the same time, 46, the latter being held retracted normally through the wedge clamp and other connecawaeae tions hereinafter described, effecting a change in the angle of incidence of the wings or permitting them to return to normal condition. To operate the vertical rudder, a foot lever 62 is pivoted about midway its length on the bar 5, and is connected at its ends by cables 63 to the opposite ends of the rudder arms 24, 'and for convenience in operating this foot lever and the control column, a seat 64 is suspended from the said portions 2 in a plane slightly rearward of said foot lever. Erected upon the portions 20f the fuselage is a pyramidal frame, consisting of four upwardly-converging bars 65, rigidly connected at their upper ends by a coupling 66, and extending downward from and rigid with the coupling is a guide rod 67.

68 is a tubular piston rod, fitting slidingly on rod 67, projecting upwardly from a piston 69 fitting slidingly in a cylinder 70, rigidly secured upon the skid 13, and communicating with the lower end of the cylinder is a pipe 71, which communicates at its upper end with a three-way valve 72, the plug 73- of the valve being secured upon a, shaft 74 journaled in the upper end or head of the control column 53, and to turn said shaft for the purpose of opening or closing said valve, a crank handle 75 is secured on the rear end of the shaft. When the valveis opened by operation of the crank handle, it establishes communication between pipe 71 and a pipe 76, leading from a compressed air tank 77 suspended by stirrups 78 from bar 5, the arrangement being such that when said-valve is opened air passes from the compressed air tank into the lower end of the cylinder and forces the piston upwardly for a purpose which hereinafter appears, reverse movement of the crank beyond its initial position establishing communication between the cylinder and the atmosphere by way of .pipe 71 and the third port 79, of the valve casing, as shown in Fig. 6. J ournaled on the coupling 66 forward and rearward, respectively, of the piston are two pairs of grooved pulleys or sheaves 79 and 80, and secured upon the stem of the piston is a bracket 81, upon which is journaled forward of the stem a pair of compensating pulleys each consisting of a small member 82 and a large member 83 fixed together. Secured forward and rearward respectively, and at the lower end of the cylinder 70, are two pairs of pulleys or sheaves 84 and 85, and secured upon opposite ends of a rock bar 86, are sets of pulleys or sheaves 88; said rock bar being disposed at the rear side of the cylinder and secured upon the front end of a horizontal rock shaft 89 journaled at its rear end in bearing 55 mounted upon cross bar 56 as shown clearly in Fig. 7. Shaft 89 is also equipped with arock-bar 90 connected by vertical rods 91 to a rock bar 92 secured rigidly on a sleeve 93 journaled on shaft 74, and carrying a hand wheel 94.

95 is a pair of cables secured at their upper ends to the large members 83 of the comensating pulleys, andextending around the pulleys or sheaves 84, and attached to the lqwer ends of said cables 95 are equalizing levers 96, and attached at their lower ends to the opposite ends of said equalizing levers are cables 97 and 98, attached at their upper ends to the front spars of the wings 28, the cables 97 being connected to said 98 at points nearer the fuselage.

/ 99 are cables which engage and ex-,

tend downward and outward from sheaves 79 and. are attached at their lower ends to the small members 82 of the compensating pulleys and at their outer ends to equalizing levers 100, and attached at their inner or upper ends to opposite ends of said levers are cables 101 and 102, which cables are attached at their outer ends to the front spars of the wings coincidentally with the points of attachment of cables 97 and 98 respectively. It will thus be seen that the cables above and below the wings converge outwardly and that the cab es of each set bear a diverging relation.

Attached to the rear spars of the wings at diflerent distances from the fuselageare lower sets of cables 103 and 104, and coincidentally attached at their outer ends to said spars, are upper sets of cables 105 and 106, said sets of cables 103104 and 105 106 converging outwardly. The inner ends of cables 103 and 104 are attached to opposite ends ef equalizing levers 107, and the inner ends of cables 105-106 are attached to opposite ends of equalizing levers 108, and attached at its opposite ends to the lower left-hand equalizing lever 107, andthe upper right-hand equalizing lever 108, is a cable 109; said icable extending over the left-hand sheave 88 and under the righthand sheave 88 of the same set, over the right-hand sheave 80, and under the lefthand sheave 85. A similar cable 110 connects the upper left-hand equalizing lever 108 to the lower right-hand equalizing lever 107, and extends over the right-hand sheave 88, under the left-hand sheave 88 of the other set, over the left-hand sheave 80, and under the right-hand sheave 85. The use of the terms left-hand and right-hand in the preceding portion of this paragraph, is with respect to Figs. 3 and 4, of the drawings. It will thus be seen that swinging the sheaves 88 in one direction about the axis of shaft 89 results in the taking up of one of the cables and in the paying out of the other cable, and that reverse movement of said sheaves 88 gives the opposite efl ect, it being understood from this that the taking up of a cable results in an upward pull through cables 105 and 106 on one of the wings and in a downward pull on the opposite wing through cables 103 and 104 attached thereto, and that the paying out of the other cable permits the first-named wing to be moved upward and the other wing to be moved downward. It will also be understood that this adjustment of the wings is accomplished by rotating the handwheel 94 in one direction or the other, power being transmitted for such operation from the hand-wheel to the sheaves 88, through the medium of sleeve 93, rock-bar 92, rods 91, rock-bar 90, shaft 89, and rock-bar 86 carrying the said sheaves 88.

Journaled on bracket 81 carried by the piston stem, is a pulley or sheave 111, and extending over the same is a doubled cable 112, attachedat its lower ends to the cables 109 and 110, as shown mostclearly in Fig. 4, the arrangement being such that upward movement of the piston shall exert a pull on cable 112 and-cables 109 and 110, and thus effect a downward pull through cables 103 and 104 on the wings, this downward movement of the wings being effected by operating the crank handle 75 so as to open communication by means of the valve and pipes 71 and 76, between the air tank and the cylinder. When the operation of the crank handle is reversed, the valve closes communication between the cylinder and the air tank. Suflicient reverse movement of the crank handle opens communication between the cylinder and the atmosphere. As this occurs the upward pressure on the wings assuming the machine is in flightforces the same upward and the pistondownward, the movement of the wings keeping the cables taut, it being of course, understood that the sheaves will be provided with customary and well known guards (not shown) for retaining the cables in place. Owing to the fact that the cables above the plane extend at a less angle to the wings than the cables below the plane, it is necessary that the lower front cables shall pay out more than the front upper cables take up because the front portions of the wings must not flex. On the other hand, it is desirable that the rear portions of the wings shall fleX upward when the wings are permitted to swing upward by exhausting air from the cylinder, this upward flexing being caused through the use of the non-compensating rear cables.

In Fig. 5, dotted lines are employed showing a wing swung upward, the central arcuate line showing the movement of the wing at the point of attachment of cables 101 and 97, and the outer and inner arcuate lines the paths which said point would tend to follow if no provision was made for paying out cable 97 and taking up out movement must and does exceed the plates 57 forming the wedge clamp hereinbefore mentioned, and said shafts 113 are provided at their front ends with long crank arms 115 equipped with grooved rollers 116 arranged within the loop of the doubled cable 112, the arrangement being such that the spreading of the wedge clamp by operation of the control column operates shafts 113 and thereby bows the two ends of the doubled cable 112 outwardly by means of pulleys 116, and as a result imparts an upward pull on the lower portions of cables 109 and 110 whereby the rear portions of the wings are warped downward for the purpose of changing their angle of incidence to the line of flight.

The described action of the control column exerts a forward pull on the lower cable 60 leading to the upper side of the horizontal rudder and correspondingly slackens the other cable 60 leading to the other side of the horizontal rudder, the column, of course, rocking at its pivotal point 54. Assuming the wings and rudders to be in the position shown, the motor is started and at the proper time the machine is released. After traveling on the ground a sufficient distance it gains headway andrises, the ascent being made more abrupt and rapid if'the operator pulls the control column rearward, to raise the horizontal rudder and increase the angle of incidence of the wings. After attaining the plane of flight desired, the control column is restored to normal position to lower the rudder and permit the wings to straighten out from their warped condition, under the pressure of the sustaining air, it being understood that while in flight and without regard to the position of the horib zontal rudder or the condition of the wings, the machine may be steered to the right or left by proper operation of the vertical rudder effected by manipulation ofthe foot lever 62. Assuming the machine tilts laterally it may be restored to proper position by reversing Warping the wings by turning the hand-wheel in the proper direction, this action rocking the bar 86 and through sheaves 88 taking up the cable between two of the levers 107 and 108 and paying out the cable between the other pair of levers. If this reverse warping'of the wings fails to instantly restore the equilibrium of themachine the upper part of the control column is swung laterally toward the high side of the machine and through the connected cable 42, effects the collapse of the wing tip at incense {s3 such side, the sprin 47 yielding slightly to pay out cable 41 su ciently to accommodate such collapsing action. It will thus be seen that provision is made to guard against dangerous lateral tilting of the machine, it being noted that the warping action will be most effective when the speed is greatest and that the collapsing of the tips will be most effective when the speed is comparatively low.

To shift the wings to a dihedral angle, the crank handle is turned to open the valve and exhaust a portion of the air from the cylinder. this resulting in the instantaneous upward movement of the wings and a downward movement of the pistonand the sheave 11 1 and the compensating pulleys, the latter being turned by the pull of cables 95 on pulley members 83, the slackening cables 99 being simultaneously wound on the small members 82 of said pulleys. By turning the crank handle to establish communication between the tank and cylinder, air enters the latter and effects downward swinging of the wings, the cables 99 turning the compensation pulleys as they unwind therefrom and winding the slackening cables 95 thereon.

Under exceptional conditions it might be desirable to set the wings at a sharp dihedral angle, for instance, where headway is lost from motor trouble, as in this case the quick exhaust of the air from the cylinder would permit the wings to rise instantly with respect to the plane of support. At the same time the angle of incidence would be decreased because of the non-compensating action of the warping cables that is to say, the cables 105 and 106 would tend to warp both wings upward at .their rear margins and thus effect a shifting of the plane of support further rearward thereof. The re-,

sult of these actions would be to start the machine forward, 71. e.' give it headway and enable the operator to regain control or to glide to the ground. If flying low at the time the danger could be diminished by admitting air to the cylinder to' restore the wings to proper sustaining position, and by increasing the angle of incidence of the wings and raising the horizontal rudder through a rearward pull on the control co1- umn.

From the above description it will be apparent that I have produced an aeroplane embodying the features of .advantage enumerated as desirable in the statement of the I object of the invention and which may be jecting laterally from each side of said fuselage, and cables for operating said wings and connected to the front and rear edges thereof from above and from below, each of the front cables being attached at its opposite ends to the same wing and each of the rear cables being attached at its opposite ends to different wings.

2, In an aeroplane, a fuselage, a wing projecting from each side of the fuselage, a plurality of cables connected to said wings from above and from below and suitably guided upon the fuselage, the lower portions of'the cables extending at greater angles to the. wings than the upper portions, and means engaging said cables to shift the wings, said means including provision for taking up and paying out the lower portions jectin laterally from the fuselage at each side t ereof and capable of swinging in a vertical plane, suitably guided cables, each overlying one wing and underlying the other and connected at its opposite ends to different wings, and means for reversely warping the rear portions of said wings simultaneously.

5. In an aeroplane, .a fuselage, a wing projecting laterally from the fuselage at each side thereof and capable of swin g in a vertical plane, suitably guided ca les, each overlying one Wing and underlying the other and connected at its opposite ends to difierent wings, and means for exerting a downward pull on the said underlying end of one of said cables and an upward pull on the opposite end of the same cable.

In an aeroplane, a fuselage, a wing projecting laterally from the fuselage at each side thereof and ca able of swin g in a vertical plane, suita- 1y guided ca les, each overlying one wing and underlying the other and connected at its oppositeends to different Wings, and means for changing the angle of incidence of the wings while the aeroplane is in flight by warping the rear portions of the Wings downward simultaneously.

7. In an aeroplane, a fuselage, a wing projecting outwardly from and at each side of the fuselage and suitably-guided cables, each overlying one wing and underlying the other and attached at its ends to different wings, the said underlying ends of the cables extending at greater angles to the wings than the said overlying ends.

' 8. In an aeroplane, a fuselage, a wing projecting outwardly from and at each side of the fuselage, suitably-guided cables, each overlying one wing and underlying the other and attached at its ends to different wings, the'said underlying ends of the cables extending-at greater angles to the wings than the said overlying ends, a yieldingly-elevated device connected to said cables and exerting a downward pull therethrough on said wings and means for diminishing the force of such pull to permit said device to move downward and the wings to swing upward while the aeroplane is in flight.

9. In an aeroplane, a fuselage, a wing projecting outwardly from and at each side of the fuselage, suitably-guided cables, each overlying one wing and underlying the other and attached at its ends to different wings, the said underlying ends of the cables eX- tending at greater angles to the wings than the said overlying ends, a yieldingly-elevated device connected to said cables and exerting a downward pull therethrough on said wings, means for diminishing the force of such pull to permit said device to move downward and the wings to swing upward while the aeroplane is in flight, and means to reverse the movement of said device to cause the said underlying ends of the cables to reverse the wing movement.

10. In an aeroplane, a fuselage, a' wing projecting outwardly from and at each side of the fuselage, suitably-guided cables, each overlying one wing and underlying the other and attached at its ends to different wings, the said underlying ends of the cables extending at greater angles to the wings than the sald overlying ends, means engaging said cables and movable to simultaneously take up one of them and thus pull upward on one of the wings and downward on the other and at the same time pay out the other cable to accommodate said movement of the wings.

ll. In an aeroplane, a fuselage, a wing projecting laterally at each side of and hingedly connected to the fuselage, a pair of guide sheaves above and a pair of guide sheaves below the fuselage, a cable extending over one of the upper guide sheaves and below one of the lower guide sheaves, a second cable extending over the other upper gu de sheave and under the other lower guide sheave, the opposite ends of-each cable being connected to different wings, a rock lever intermediate the upper and lower sets of sheaves, and means whereby rocking movement of said lever in one direction shall take up one of said cables and pay out the other and rocking movement in the opposlte direction shall take up the lastnamed cable and pay out the other cable.

12. In an aeroplane, a fuselage, a wing pro ecting laterally from each side of said fuselage, and cables for o erating said wmgs and connected to the out and rear edges thereof from above and from below, each of the front cables being attached at its opposite ends to the same wing, and extending at a greater angle to the same from below than from above, said front cables being provided with differential winding means for taking up the lower portions thereof faster than the upper portions thereof.

13. In an aeroplane, a fuselage, a wing projecting laterally from each side of said fuselage, a rear horizontal rudder, cables for operating said wings and connected to the front and rear edges of the same from above and below, a doubled cable connected at its opposite ends to, points on said rear cables, means for spreading said doubled cable for causing the rear cables to warp the wings, and a control column provided with connections for simultaneously operating said rudder and said spreading means.

' 14:. In an aeroplane, a fuselage, a wing projecting laterally from the fuselage at each side thereof, and capable of flexing instrumentality of said first-named cables.

15. In an aeroplane, a fuselage, a wing projecting laterally from the fuselage at each side thereof, and'capable of flexing along its rear edge, suitably guided cables attached at their outer ends to the rear portion of the wings, a doubled cable'suitably guided, and movable means for applying pressure on said doubled cable at angles to its length to cause it to pull the rear portions of the wings downward through the instrumentality of the first-named cables.

16. In an aeroplane, a fuselage, a wing projecting laterally from the fuselage at each side thereof, and capable of flexing alon its rear edge, suitably guided cables attac ed at their outer ends to the rear portion of the wings, a control column movably mounted on the fuselage, a rocking bar, and means carried by the rocking bar, actuated by movement of said column to warp the rear portions of said wings downward simultaneously through the instrumentality of the said cables.

17. In an aeroplane, a fusela e, a wing projecting laterally from the selage at each side thereof, and capable of flexing taneously warp the rear portions of the wings downward.

18. In an aeroplane, a fuselage, a wing projecting laterally from the fuselage at each side thereof, and capable of flexing along its rear edge, suitably guided cables attached at their outer ends to the rear portion of the wings, a doubled cable suitably guided, 'a wedge clamp mounted on the fuselage and consisting of two members, a pivoted control column fitting in the wedge clamp and adapted when moved in one direction to force the members of the clamp apart, and means wherebysuch movement of the members shall efiect the downward warping of the rear portions of the wings through the instrumentality of the doubled cable and said first-named cables.

19. In an aeroplane, a fuselage, a wing projecting laterally from the fuselage at each side thereof, and capable-of flexing along itsrear edge, suitably guided cables attached at their outer ends to the rear portion of the wings, a doubled cable suitably guided, a pair of rock-shafts, carried by the fuselage, provided with crank arms engaging the doubled cable at opposite sides of its guided point, a pivoted control column carried by the fuselage, and means whereby proper movement of the control column shall rock said shafts and cause the cranks thereof to warp the rear portions of the Wings downward through the instrumentality of the doubled cable and said first=named cables.

20. Inan aeroplane, a fuselage, a wing projecting from the fuselage at each side thereof, and capable of swinging vertically, suitably-guided cables, each overlying and attached to one wing and underlying and attached to the other wing, a rockshaft, and means whereby turning movementof the said shaft in one direction shall exert a pull on opposite ends of one of said cables, and turning movement of said shaft in the opposite. direction shall exert-a pull on the opposite ends of the other cable.

21. In an aeroplane, a fuselage, a wing projecting from the fuselage at each side thereof, and capable of swinging vertically, suitably-guided cables, each overlying and attached to one wing and underlying and attached to the other wing, a rock-shaft, suitably guided means holding each of said cables bowed in opposite directions and crossed between their bowed portions, and

means whereby turning movement of the rock-shaft in one direction shall cause the means holding the cables bowed to apply pressure on one of said cables and thereby exertan upward pull on one wing anda downward pull on the other and at the same time pay out the other cable to accommodate such movements of the wings.

22. In an aeroplane, a fuselage, a wing projecting from the fuselage at each side thereof, and capable of swinging vertically,

23. In an aeroplane, a fuselage, a wlng projecting laterally at each side of and from the fuselage and pivoted for vertical movement, a tank containing fluid under pressure, a cylinder connected with the tank, a piston in the cylinder, a valve, whereby fluid may be permitted to pass from the tank into the cylinder or from the latter to the atmosphere, and means whereby movement imparted to the piston by fluid entering the cylinder shall exert a downward pull on the wings, and whereby said wings shall be permitted to swing upward through the 'flow of fluid from the cylinder.

24. In an aeroplane, a fuselage, a-wing projecting laterally at each side of and from the fuselage and pivoted for vertical movement, a tank containing fluid under pressure, a cylinder connected with the tank, .a piston in the cylinder, a valve whereby fluid may be permitted to pass from the tank,

into the cylinder or from the latter to the atmosphere, a pair of equalizing pulleys, movable with said piston, and each composed of a small and a large member, a cable engaging each small member of the equalizing pulleys and connected at its opposite end to one of said wings from a point higher than the hinged end of the same, a second pair of cables, each engaging one of the large members of the equalizing pulleys and connected at its opposite end to one of the wings and extending thereto from a point a greater distance below the hinged point than said first-named cables extend above the hinge point.

25.. In an aeroplane, a fuselage, a wing projecting laterally at each side of and from' to the rear portions of different wings, a second pair of upper guides, a second pa1r oflower guides, a pair of compensating pulleys between said second pairs of guides, each pulley comprising a small member'and a large member, a pair of cables, extendmg over the second pair of upper guides and attached at their lower ends to the small members of the pulleys and connected at their opposite ends to the front portions of the wings, another pair of cables extending under the second lower pair of guides and attached at their upper ends to the large members of said pulleys and connected at their opposite ends to said wings,and means for holding the wings yieldingly depressed' 26. In an aeroplane, a fuselage, a wing rojecting laterally at each side of and f rom the fuselage, and pivoted for vertical movement, and capable of flexing along its one of the upper guides and under one of the -lower guides and connected at its ends to the rear portions of different wings, a similar cable extending over the other upper guide and the other lower guide and connected at its ends to the rear portions of d1fferent wings, a second pair of upper guides,

a second pair of lower guides, a pair of com-,

pensating pulleys between said second pairs of guides, each pulley comprising a small member and a large member, a pair of cables, extending over the second pair of upper guides and attached at their lower ends to the small members of the pulleys and connected at their opposite ends to the front portions of the wings, another pair of cables extending under the second lower pair of guides and attached at their upper ends to the large members of said pulleys and connected at their opposite ends to said wings, and yielding means exerting a downward pull on said wings through the ends of the cables which underlie the Wings.

27. In'an aeroplane, a fuselage, a wing projecting laterally at each side of and from the fuselage and pivoted for vertical move- :ment, and capable of flexing alon its rear margin, a pair of guides above the center of the fuselage, a pair of guides below the center of the fuselage and a greater distance below the plane of the wings thanthe firstnamed wguides, a cable extending over one of the upper guides and under one of the lower guides and connected at its, ends to the rear portions of different wings, a similar cable extending over the'other upper guide and the other lower guide and connected at its ends to the rear portions of different wings, asecond pair of upper guides, a second pair of lower guides, a pair of comper guides an of guides, each pulley comprising a small member and a large member, a pair of cables, extending over thesecond pair of upattached at their lower ends to the small members of the pulleys and connected at their opposite ends to the front portions of the wings, another pair of cables extending under the second lower pair of guides and attached at their upper. ends to the large members of said pulleys nd connected at their opposite ends to said wings, a guide movable with the compensatin pulleys and a cable extending over said guide and attached at its lower ends to the first-named pair of cables. I

28. In an aeroplane, a fuselage, a wing projecting laterally at each side of and from the fuselage, and pivoted for vertical movement, and capable of flexing along its rear margin, a pair of guides above the center of the fuselage, a pair of guides below the center of the fuselage and a greater distance below the plane of the wings than the firstnamed guides, a cable extending over one of the upper guides and under one of the lower guides and connected at its ends to the rear portions of different wings, a similar cable extending over the other upper guide and the other lower guide and connected at its ends to the rear portions of different wings, a second pair of upper guides, a second pair of lower guides, a pair ,of compensating pulleys between said second pairs of guides, each pulley comprising a small member and a large member, a pair of cables, extending over the second pair of upper guides and attached at their lower ends to the small members of the pulleys and connected at their opposite ends to the front portions of the wings, another pair of cables extending under'the second lower pair of guides and attached at their upper endsto the large members of said pulleys and connected at their opposite ends to said wings, a cylinder, a piston in the cylinder, a stem for the piston carrying said equalizing pulleys and the last-mentioned guide, and means for admitting fluid under pressure to the cylinder to move the piston in one direction or for permitting fluid to escape from the cylinder to permit the piston to be moved in the opposite directio 29. In an aeroplane, a fusela e, a wing projecting laterally at each si e of and hingedly connected to the fuselage for sw nging movement in a vertical plane, cables suitably guided at points above the plane of the wings and each extending downwardly and, outwardly from one of said points above and. connected at its outer end 'to one of said wings, a second pair of cables suitably guided at points a greater distance below the plane of the wings than the 159 first-named set of guiding points are disposed above such plane and extending upwardly and outwardly from their guiding points under and connected at their outer ends to said wings, vertically movable means I between said first-named and last-named sets swinging movement in a vertical plane, ca-' bles suitably guided at points above the plane of the wings and each extending downwardly and outwardly from one of said points above and connected at its outer end to one of said wings, a second pair of cables suitably guided at points a greater distance below the plane of the wings than the first-named set of guiding points are disposed above such plane, and extending upwardly and outwardly from their guiding points under and connected at their outer ends to said wings, vertically movable means between said first-named and lastnamed sets of guiding points, means for shortening the first-named cables and lengthening the last-named cables when the said device moves downward and for lengthenmg the first-named cables and shortening the last-named cables when said device moves upwardly, a cylinder containing air under pressure, a piston in the cylinder carrying said vertically movable device, means for supplying fluid under pressure to the cylinder to force the piston upward and means for exhausting fluid from the cylinder to permit the wings to swing downward.

In an aeroplane, afuselage, a wing pro ecting laterally at each side of and hingedly connected to the fuselage for swmgmg movement in a vertical plane, and two sets of compensating pulleys, each consisting of two members of different diameter, cables suitably guided at points above said pulleys and above the plane of the wmgs and extending downwardly and outwardly above and connected to the wings and each attached at its opposite end to one of the small members of the-compensating pulleys, a second pair of cables suitably guided below said compensating pulleys and a greater distance below the plane of the wings than the first-named guiding points are disposed above such plane, and extending upwardly and outwardly from their guided points under and connected to said wmgs, and attached at their opposite ends to the larger members of said compensating pulleys and engaging the same at the cables engage the small members of said compensating pulleys.

'- 32. In an aeroplane, a fuselage, a wing projecting laterally at each side of and hingedly connected to the fuselage for swinging movement in a vertical plane, two sets of compensating pulleys, each consistin of two members of different diameter, ea les suitably guided at points above said pulleys and above the plane of the wings and extending downwardly and outwardly above and connected to the wings and each attached at its opposite end to one of the small members of the compensating pulleys, a second pair of cables suitably guided below said compensating pulleys and a greater distance below the plane of the wings than the first-named set of guiding pulleys are disposed above such plane, and extending upwardly and outwardly from their guided points under and connected to said wings and attached at their opposite ends to the larger members ofsaid compensating pulleys and engaging the same at the same side of their axes as the first-named cables engage the small members of said compensating pulleys, means holding the compensating pulleys at a predetermined height, and through the said secondset of cables holding the wings against accidental upward movement, and means to release said compensating pulleys during flight to permit the wings to swing upward and impart downward movement to the compensating pulleys and incidentally rotate the same to pay-out the second set of cables from the larger members and take up the other set of cables by winding them upon the smaller members of compensating pulleys.

33. In an aeroplane, a fuselage, a wing projecting laterally at each side ofand hingedly connected to the fuselage for swinging movement in a vertical plane, two sets of compensating pulleys, each consisting of two members of different diameter, cables suitably guided at points above said pulleys and above the plane of the wings and extending downwardly and outwardly above the same, a lever attached midway its length to the outer end of the downwardly and outwardly extending portion of each of said cables, a pair of cables attached at their inner ends to the opposite ends of each lever and at their outer ends to the wings at different distances from the hinge points thereof, the opposite ends of said first-named cables being attached to the small members of the compensating pulleys, another pair of cables suitably guided at points below the compensating pulleys and extending upwardly and outwardly from said guide points and attached to the largermembers the same at the same side of their axes as same side of their axes as the first-namedthe first-named set of cables engage the small members of said pulleys, levers attached midway their length to the .outer ends of the cables guided at points below the compensating pulleys, and a pair of cables attached at their inner ends to the opposite ends of each of said last-named levers and at their outer ends to the wings at difierent distances from the hinge points thereof.

34. In an aeroplane, a fuselage, a wing projecting laterally from and at opposite sides of the fuselage, collapsible tips for said wings, a suitably guided cable connected to saidtips and looped at a suitable point, yielding means connected to the looped portion of the cable and normally holding the tips expanded, and means for collapsing either of the said tips in opposition to said yielding means.

35. In an aeroplane, a fuselage, a wing projecting laterally from opposite sides of*- said fuselage, a collapsible tip at the outer end of each of said wings, means acting to hold said tips normally yieldingly expanded, suitably guided cables operatively connected at their outer ends to said tips for cables.

36. The combination in an aeroplane having wings, and a horizontal rudder, a wedge clamp, a control column pivoted above the wedge clamp and adapted when swung rearwardly at its upper end to enter the clamp and force the sides thereof apart, means whereby said wedge clamp when its sides are forced apart, shall warp the rear portions of the wings downward and crossed connections overlying and underlying and connected at their rear ends to said rudder and respectively attached at their front ends to the control column below and above the pivotal point thereof.

In testimony whereof I aflix my signature, in the presence of two witnesses.

JOHN WATTS. Witnesses:

M. K. PRESTON, G. Y. THoRPE. 

